Magnetic compass indicating system for aviation trainers



July 20, 1948. lc-A. KAIL MAGNETIC COMPASS INDIGKTING SYSTEM FOR AVIATION TRAINERS 4 Sheets-Sheet 1 Filed July 30, 1943 KARL- A. KAIL INVENTOR.

ATTORNEYS.

Filed July 30, 1943 July 20, 1948. K A KA|| 2,445,673

MAGNETIC COMPASIS fNDICATING SYSTEM FOR AVIATION TRAINERS 4 Sheets-Sheet 2 I08 I02 98 84 I06 s2 '07 I04 I00 58 FIG.- 2'

I KARL A. KAI L INVENTOR.

M/VT

AT T O BNEYS y 1948. K. A. KAIL 2,445,673 MAGNETIC COMPASS INDICATING SYSTEM FOR 7 AVIATIOB TRAINERS Filed July 30, 1943 4 Sheets-Sheet 3 KARL A. KAIL INVENTOR.

AT TORNEYS.

July 20, 1948. A, KA|| 2,445,673

MAGNETIC COMPASS INDICATING SYSTEM FOR AVIATION TRAINERS Filed July 30, 1943 4 Sheets-Sheet 4 KARL A. KAIL. INVEN7"OR..

ATTORNEYS.

Patented July 20, 1948 I MAGNETIC COMPASS INDICATING SYSTEM FOR AVIATION TRAINERS Karl A. Kail, Montrose, Pa., assignor to Link Aviation, Inc., Binghamton, N. Y a corporation of New York Application July 30, 1943, Serial No. 49.6,738

7 Claims. 1

functioning of the compass in a real plane at any.

point upon the earth's surface may be simulated.

Another object of my invention is to provide a compass system for a grounded aviation trainer which is completely independent of the earths magnetic field, and to provide in such a system means whereby any variation may be introduced into thesystem.

In order that the following description may be more readily understood reference is made to the accompanying figures wherein Fig. 1 shows a general view of the trainer and instrument system which my present invention comprises.

Fig. 2 is a diagrammatic view of the instrument system of this invention.

Fig. 31s a detailed view of the magnetic compass variation control;

Fig. 4 showsan alternate system for introducing the desired variation into the compass system.

Reference is now made to Fig. 1 which shows a trainer of the type disclosed'in U. S. Patents 1,825,462 and 2,099,857. These trainers, which are of the type manufactured by Link Aviation Devices, Inc, Binghamton, New York, comprise a fuselage 10 which is mounted upon a universal joint (not shown) positioned near the central part of the floor of the fuselage. A pair of bellows I2 known as the elevator bellows are provided and through a system of vacuum, valves and linkages these-bellows may be made to pitch fuselage ill in simulation of the climbing and diving of a plane inactual flight. A second pair of bellows, known as the aileron bellows, are used to bank the fuselage l laterally in simulation of the'banking of aplane in actual flight. Only one of these aileron bellows is shown and it is designated l4. Still referring to Fig. 1 it will be seen that atriangular base "5 is provided, and rigidly attached thereto is a lower bearing housing l8.

Formed integrally with the upper end of this hearing housing is an exterior annular groove 20. Inside lower bearinghousing l8 and rigidly aflixed theretois ring gear 22. Base l6, lower housing I8, annular groove 20 and ring gear 22 are fixed in relation to the floor upon which base It rests. Upper bearing housing 24 is rotatably mounted with respect to lower housing l8 by means of a suitable bearing arrangement and rigidly attached to housing 24 is platform 26 upon which rests the triangular tower 28 which holds the fuselage I0 and other associated apparatus. Rigidly aflixed to and depending from platform 26 is turning motor 30 which has an output shaft upon which is rigidly affixed a wheel 32 which also is grooved. Turning ,belt 34, it will be noticed, wraps around groove 20 integral with fixed lower bearing housing l8 as well as around the output wheel 32 of turning motor 30. Whenever the student in the trainer presses one of the rudder pedals (not shown) therein, turning motor 30 is actuated and the output wheel 32 rotates in a direction dependent upon which rudder pedal is pressed. The friction between groove 20 and belt 34 on the one hand, and wheel 32 and. belt 34 on the other, is sufficiently great to prevent slipping therebetween, and consequently, wheel 32 travels along belt 34 causin motor 30, platform 26, tower 28, fuselage l0 and upper bearing housing 24 to rotate in simulation of the turning of a plane in actual flight.

Also seen in Fig. 1 is an operators desk 35 which has placed thereupon a map 36 over which recorder 31 travels. A detailed description of recorder 31 may be found in U. S. Patent 2,179,663, and as there disclosed it moves forward over the map or chart 35 to simulate the forward travel of the trainer, and whenever the trainer fuselage I0 is turned the recorder 31 turns its direction of travel on the map. The recorder also has an inking wheel (not shown) which makes a line along the map as the recorder travels .over it. By a reference to the position of the inking wheel upon the map 36 the operator may determine the exact simulated location of the trainer.

All of the foregoing apparatus forms no part of my instant invention except when combined with features to be later described, and therefore, a more detailed description is omitted, but for a thorough explanation thereof reference is made to the above-mentioned United States patents.

Magnetic compass system In a plane in flight one'of the most relied upon instruments is the magnetic compass which, as is commonly known, comprises a magnetized bar which, when freely suspend'eihas its longitudi- I ,nal axis parallel to the lines of force of the earth's 3 magnetic field. Inasmuch as the real North Pole and the magnetic North Pole are not at the same place, in most localities the compass does not point toward true north because the direction from most points upon the earths surface to the true North Pole differsirom the direction of the magnetic North-gP-cleq The angular difference, between the directions of true north and--magnetic north at any place is known in navigation as the magnetic variation of the place and is lo called westerly variation or easterly variation depending upon Whether magnetic northylieswtothe west or east of true north.

In actual flight, the pilot ornavigator;knowing the general vicinity of the plane; by applying the magnetic variation for that vicinity, as determined from well-known charts to;thewompassv reading can ascertain the true heading of the plane. Over flights of any considerable distance this magnetic variation usually varies and the pilot or-navigator must apply the'diffe'rent varia-' tionsas the p1ane makesp-rogressdn its I flight.

Trainers of theetype -being-considered-* arerela tively--- fixedat a given point" upon I the earth's" surface and even though they are fixed; flights: s

over considerable distancesas before mentioned may-be simulated therein; In order that the exact conditions which would -occur'in* actual flight may be reproduced insuch. a trainer itisclear-thatmeans should be-provided for simulatin'gthe various magnetic variations to which the compass ina plane actually making the-simu latedflight would lee responsive; If the compass-were merely installedin the/trainer, itis clear that although the compass would respond to'the turning -of the trainer the variation componentf would be constant and equal tothe-varia tion of the localitywhere the trainer is i erected;

The following means may be used-in order to introduce difierent variationsinto the compass-in the trainer as the simulated position of the trainer-determined by 'a'referenceto the recorder 31 'upon; the map '36 changes; even-though the trainer actually rnakes no iiorward progress. The

student navigator; knowingthe approximate as- 5 sumed geographical 1002.1'ii0'fif of --th'e trainer will" therefore he forced to resort-to hischarts to-- determine what-the variation would be if a plane were actually flying-at the point- -where the trainer-is assumed-to be, and "then 'he must applythiswariation to the readingof the com pass}- -in the trainer in order-to determinethe true} assumed heading "ofthe'tra-i-nerr- Reference is made toFigs: 1 and 2.-'- It'h'asbeen toflower" gear housing I 8 and therefore -does not rotate' -as the platform' -26', tower 28-*and fuse1age I Il-rotate; Meshingwith gear -2 2 ie an antiba-ck lash-gear-flt which is rigidly affixed to the lower-- end ofvertic'al shaft 32. 'In Fig:l;it willtie-seem that this vertical shaft enters aboxlike' structure 44 which is referred to in the art as the heading--- ge arbox; The mechanism containedin-thisgear box'is' enclosed 'in dotted lines-in"Fig.-'2. It will' be seen that inside the heading gear box-"Gland fixed upon verticaljshaft'AZ-is a gear flifi which meshes with" a" smaller gear 4%." This-last-men tioned gear is fixed upon a second verticalshaft 50 which has rigidly mounted upon-.itsaupper end beyel geartZ which meshes witha second bevel detail'in the 'copending application of Gunne 4 Lowkrantz and myself, Serial No. 406,056 filed August 8, 1941. It is to be noted that the recorder 31 is connected to the wind drift instrument 58 by means of electrical connections 62 and 64 which are carried by a single cable 65. The wind drift instrument as explained in the mentioned copending application provides meansgforxmaking-the speed of the recorder 31*responsive to the changing assumed ground speeds of the trainer.

Referring; again-to-Fig. 2, it will be seen that rigidly afiixed upon the upper end of shaft 42 is a gear 68. This gear is in mesh with gear 70 which is-likcwisefixedupon the lower end of a third vertical ;shaft:'l2;'- My variation setting mechanism is designated generally in this figure by M and iuwillbe. seen that a fourth shaft I6 is mounted in the upper end thereof. The upper end of this shaft enters flexible shaft connector it where the rotation of shaft 16 is transferred to=flexible shaft 84* To theupper end 'of'flexible shafting-tis fixed worm86 which" engages worm; gear -88.- A vertical shaft 905s fixedly attach'ecl to worm gear tii'and holds bar magnet 92 which: is afiixed to the lower end of shaft 90. Disposed. below bar magnet 92 is' a=.second 'bar'magnet 94 which is mounted upon the input i-shaft'JSGLof ax transmitting magnesyn, dcsignatedngenerallyz by-el; the housing of which is designated as 98.

th'e transmitting magnesyn to the receiving magnesyn designated generally by IIl'I and having -a housing" IilZ-andan output shaft I04" upon which is rigidly afiixed pointer I 06 Which movesover dial I63 which-is marked in thecon ventional compassdialmanner. Pointer lflfi 'and dial I08 form a simulated remote indicating-com pas's designated by- I 01; andfas seen inFigul, is-

located upon the instrument panel-in fuselageis rotated through a given angle with TESDGCtitQ-a.

its housing '98 the I output shaft I 04 of" the receiving magnesyn rotatesthrough' the samel-angle" and in a given direction with respect'to' it"shousing I02, the direction of the rotation-being de pende'nt upon: the particularwiring circuit employed.- It should be-particularly noticedthat the position of I the magnetic bar 94' attached-to input shaft 9655 independent of the-earth s mag netic field and is governed solely by the: position; of bar magnet 92."

As seenin'Fig. 1, whenthe trainer rotates the heading-gear box A i-rotates with-'platf-orm-l'b and-inasmuch as gear -22 is stationary; gear'fll wilL as it moves around gear 22,rotat'e'vertical shaft 42' and gear 68 -Which*w-i11"then' cause gear ill-and vertical shaf-t-lr-to-rotatei- A dtailed descriptionof variation I contro1-14 will be-hereinaftergiven; it being sufficient at thispoint-to state that-when in operation; arotation of shaft -72 causes variation-control to rotate and-shaft? 164s also rotated; This rotation is transferred to flexible shaft 84" by connector 18 and worm is turned-which drives the worm gear 881- Dcpendinggshaftdflis rotated'with worm gear-=88" and, therefore," the-position" of permanent jbarmagnet ems-changed. I

'If bar magnet 92 were not moved by-the rota:

tion'of the trainer through'the aforedescribed i system itwill be understood'that inasmuch as it is attached to the trainer fuselageits' rotationwould be equal to and in the same direction as the rotation of the fuselage. However, the abovementioned gears and associated parts comprise such ratios and directions of response to the movements of the trainer that when the trainer is rotated bar magnet 92 is rotated by these gears and associated parts through an angle equal to and in the opposite direction of the rotation of the fuselage, and therefore, bar magnet 92 remains fixed in its position relative to the base I6 of the trainer. The rotation of bar magnet 92 caused in the first instance by a rotation of the trainer is overcome by the take-off system being described.

Inasmuch as bar magnet 94 is controlled by magnet 92 it will be realized that it, too, remains fixed even though the fuselage is rotated. However, magnesyn, transmitter housing 98 rotates with the trainer fuselage, and therefore, there is a relative angular movement between the housin 98 and its input shaft 96 equal to the angle through which the trainer fuselage is rotated. The output shaft I04 of the receivin magnesyn is therefore rotated through an angle equal to the angle through which the trainer fuselage is rotated, and pointer I06 moves across dial I63 through an equal angle. The new assumed heading of the trainer is therefore shown by compass I01, except, of course, for the variation which has been previously set into the system by the operator, as will hereinafter be described.

Reference is now made to Fig. 3 which shows the detailed construction of variation control designated in Fig. 2 by I4. It will be seen in Fig. 2 that vertical shaft 12, to which reference has been previously made, enters the lower housing H6 of the variation control and is attached thereto by means of a set screw H2 so that shaft I2 and lower housing H0 always rotate together. Locking knob H4 is integrally formed with a vertical shaft I I6 which has a lower threaded portion I I8 which cooperates with a threaded portion in the lower end I20 of the housing III]. A look nut I22 is also provided. Shaft I I6 passes through shoulder I I1 integral with lower housing I I0 and rigidly affixed to the upper end of shaft I I6 by means of a set screw I24 is an eccentri cam I26. An L slot I29 is cut in the portion I28 of the housing IIO adjacent eccentric cam I26 so that by means of locking knob I I4 cam I26 may be used to lock the threaded portion I28 of housing IIO with the threaded portion I30 of upper housing I32. Formed integrally with shoulder III of lower housing III! is a centrally disposed hollow member I34 which receives an oilite bearing I36 pressed upon the lower turned down end I31 of shaft I6. It is to be noticed that shaft I6 just above the turned down end issplined and the uppermost part I38 of housing I32 contains a bearing I40 which is adapted to receive splined lower end of shaft I6. A knurled ring I42 is affixed to the lower end of upper housing I32 by means of set screws I44 and a graduated scale I46 is affixed to knurled portion I42 by means of set screws I46. A second graduated scale I50 is aflixed to the outer lower end of lower housing IIO. This scale, it will be noticed, is graduated from zero in increments of 36 through 180 in both direc tions from the zero mark while scale I46 has two series of graduations, the upper one reading from zero through 36 in a counterclockwise direction and the lower one graduated from zero to 36 clockwise. One complete rotation of upper housing I32 moves the lower edge I52 of upper housing up or down scale I50, depending upon the.

With the previously described apparatus, it

should be understood that a rotation of knurled portion I42 to the right as seen in Fig. 3 or clockwise as seen from below will cause a rotation of scale I46 and of upper housing I32. Lower housing IIO with its threaded portion I28 remains stationary while upper housing I32, by the coaction of threaded elements I28and I30, will move upwardly as shown in Fig. 3. Such a movement rotates splined shaft I6 and flexible cable 84, worm 8'6, worm gear 88 and permanent-bar magnet 92. Magnet 94 will follow magnet 92 and compass pointer I06 will be moved counterclockwise as seen in Fig. 2, indicating a westerlyvaria-w tion. The knurled portion I42 may be moved the correct amount to set in the desired varia tion by a reference to the upper series of graduations on scale I46, viz., those on the scale marked W. When the lower'edge :I52 of scale I46 is exactly across the graduation-s upon either side of the zero mark of scale I50 and the letter W is exactly above the vertical line I54 on scale I50, no variation easterly or westerly is introduced into the system. If the knurled portion I42 is rotated clockwise so that the numeral 5 on the W scale is immediately above vertical line I54 and the upper numeral 36 on scale I50-is not visible, 5 of westerly variation have been introduced into the system and the compass pointer,

I06 is moved 5 counterclockwise of theposition it would occupy if no variation were introduced into the system. If the numeraldwere above vertical line I54 and the number '72 were visible but 108 was not visible, 77 westerly variation would be set into the system. In this manner, any desired westerly variation may be introduced into the compass indication and by turning knurled portion I42 counterclockwise and making corre-' sponding readings any desired easterly variation may be introduced. In the event an easterly variation is introduced the compass needle I06 will of course be moved clockwise across compass rose I08, the angular movement beingdependent upon the magnitude in degrees of the.

tions into the system lock nut I22 must be screw down toward locking knob I I4 and locking knob I I4 is rotated until cam I26 does not bear against the inside of the upper threaded portion I28 of housing IIO. Upper housing I32 may then .be rotated to introduce the desired variation into the system, and then locking knob I I4 is rotated until cam I26 again locks the threaded portion-s I28 and I30 to prevent relative rot-ation therebetween and the lockingv nut I22 is screwed tight. As previously stated, when locking piece I I4 is so placed the rotation of shaft I2 caused by the rotation of the trainer rotates lower housing I I0 which, because of the locking action of cam I26, rotates upper housing I32 which in turn rotates splined shaft I6, and the parts shown in Fig. 2 connected to the upper end of this shaft. a

In order that my aforedescribed compass'may be properly synchronized, the trainer is placed'on an assumed easterly heading. Locking knob H4 is turned to disengage cam I26 from the inside ofthe ithlGQdB'dPOltlOhL'. I 28 or -lower housing ;I I ll andrbyzmea'ns of knurledportion I42 upper housingi'i32 :is rotated .uritil thecletters W and 'E- on i scale Scare directly above vertical line the of scalaliifl and the lower-edge I52 of scale it isIeXactlyabQVethe horizontal lines upon either trainer turns clockwise -:a given number of -de-- greess as "toward the south, byxmeans of 'my describedrsystemz the compass needle-xlefi'turns the same "number iofz degrees clockwise; thus indicating'sthe new assumedheading of the trainer. Of courseran? opposite turning of the trainer turns the compassneedl'e I06 counterclockwise through the sameznumberof degreesras the turning of the trainer,"andicompass. lfl'lindicates the new assumed heading ofthe trainer.

Let usassume that a fiight is to be practiced from' Binghamton; New York, having a westerly variation (if-approximately 10 to San Francisco, Oa1ifornia, where' the variation: is approximately 18 east; The-rassunied trainer heading and compass-indications are synchronized as previously stated: By meansiof locking knob" I I'd the two housings l In 211114.132 are unlocked; upper housing il32" is rotated'clockwise as seen from below untll' the' num'eral of thezupper series of numerais-rcn seaiei- I46 is immediately above the verti'callirie 154 Of scale-150. The upper number 36"onscale' I50-should not be'visible. The compass will thenreadlOO when. the trainer is'on a dueeast hea-ding just as the compass in a real pl'ane at BinghamtomNew York, reads 100 when th'e plane is'heading due east. As the trainer is rotated b'ythe student'tofly westwardly the westany variation of 10 will be maintained. The stu'dent'inthe'trainer desiring, let us say, to fly due wesn by anrefe'rence-tohis chart will learn that the variation at Binghamton' is 10, and therefore *to fly a true'heading of 270 he must fiy the Ptrainer avail-assumed compass. heading of '280,"and'he 'wlll' do so; As therecorder 31 travels: over map3G' tOWard'th'e'upperleft in Fig. 1, indicating an assumed westwardlytravel of the trainer, the instructor, by referring to his chart of "magnetrc'variations in the" United States will changewthe setting of upper housing I32 with respect to iower housing H0 in orderthat the correct variationfcr'the assumed position of the trainer at any time will be introduced into the systemi As the recordershows that the trainer is assumed to ibe near'South Bend, Indiana, where the-vafiatlonfls aero; the variation as set in by variationhontrol "Id should be reduced to zero andasth'etrainer continues its simulated westward flight-an easterly variation is introduced until. when therecorder shows that the trainer-is at SanIFr'ancisco an easterly variation of 18 has been intr'oduced into the system. The navigator in thettrainer knowing the approximate assumed location of the :trainer throughout the whole flight because-he-hasnavigated the trainer across'the country will by areference to his magneticvariation-chart determine at what reading of 'the compassthetrainer should be flown, ex-

actly as though-hewere navigating a plane actuallyv taking the simulated flight.

It will be seen, therefore; that by-means of my invention the magnetic variation of a compass in a plane at anyplace upon the earths surface maybe introduced intoa compass in a grounded aviation trainer, thereby requiring the same corrections to bemade by the student navigator in the trainer as-he would have to make if he were actually flying at the point where the trainer is assumed to be.

Reference is now made to Fig. 4 which shows another embodiment of myinvention which provides means for introducing into the reading of the simulated magnetic compass in the trainer the magnetic variation of: the assumed geographical location of the trainer upon the earth's surface. It will be'seen in that figure that there is provided in placev of variation control mechanism designated generally by, T4 in Fig. 2 a-diiferential.

designatedv generally by 280. As seen in Fig. 4, the :primary input. shaft of this differential is the shaft I2 which has'been previously described and the output 'ofithe. diiferentialris .the previouslydescribed shaft 76.1 It will'bereadily understood that a rotation of the trainer fuselage It! causes a rotation of'the input shaft I2 and of the output shaft 76 and; therefore, pointer I05 moves across dial Idtin the same direction as the turning of the trainer'and, therefore, by means of compass Hi! the compass heading of the trainer may be ascertained by the student navigator.

Also seen in is the secondarydrive 282 of the variation diifer'ential 288, this secondary drive being rigidly affixed to the yoke 28% of difierential res and taking the form of an antibacklash worm gear. Worm 285 is .formed'integrallywith-the output shaft 28B of variation Selsyn-type receiver designated generally by 299.. The housing of this receiver isnumbered zez and is connected by means of wires contained incable'294 to a plurality of the pins I94 each of which is electrically connected to one of the slip rings designated generally by H32. Each of the brushes I98 carried by brush block itl' which is held stationary inside lower bearing housing. is contacts one of these slip rings and is connected by means of wires contained in cable 296 :to the housing 2&8 of variation selsyn type transmitter designated generally by 39? The input shaft of this transmitter is designated by 332 and has rigidly aflixed thereupon a spur gear sa t which mesheswith a larger spur gear 3% which is turned by variation crank Whenever crank 3&6 is turned spur gear 3 I 9 is likewise moveol'as is the gear train designated generally by M2 which rotates variation control scale This variation control scale is graduated from zero through 580 in both directions and a suitableindex mark (not shown) is provided for cooperation therewith.

Variation transmitter t-"itii'i, variation receiver 2% and the previously-described electrical connections therebetween comprise a well-known system whereby a rotation of theinput shaft 362 through a given angle rotates the output shaft 288 of the receiver 292 throughan equal angle and in the desired direction, the direction of rotation being dependent upon the specific arrangement of wiring employed. It will be understood, therefore, that a rotation of variation control crank 3G8 rotates the input shaft 3% of the trans 1 turned, thereby causing a rotation of the yoke 284:

' 9 of the differential 280 and of the output shaftlfi of this differential. j Flexible shafting 84 istherefore rotated as is worm 86 and worm; gear 88 which-of course results in .a m'ovement of .bar magnet 92. ,Bar -magnet 94.;will likewise be turned and, as previously described, the pointer I06 ,will move over dial I00.

The same rotation of variation controlcrank 308 which moves pointer. I06 simultaneously moves variation scale 3I4 so that the operator may know the amount of movement imparted to the compass needle I06 by the rotationlof-variation control 308.

When the instant embodiment of my invention is employed the system is synchronized in the following manner: i

The trainer is placed upon an assumed easterly heading, flexible shafting 84 is disengaged from worm 86 and bar magnet 92' is rotated until the compass pointer I06 is at 9,0}? or indicatesa due east heading. Flexible "shaft 84 is then, reengaged with wormilfi. Gear 304 is then disengaged from gear 306 and variation crank {3001s rotated until the zero mark on variationscale 3| 4 is exactly opposite the index mark (notsh'oIwn). Gear 304 is then reengaged with gear 306.

These steps having been taken. the trainer is then onan assumed easterly heading orheading of 90 and inasmuch as no assumed variation is set into the system the pointer I06properly points at 90 or due east. Thereafter a rotation of the trainer a given number of degrees, as toward the south, turns compass needle I06 through the same number of degrees clockwise and of course an opposite turning of the trainer likewise correctly turns the needle I05 through the same number of degrees as the turning of the trainer except that in this instance the turning of the needle I06 will be counterclockwise. It will be readily understood that by means of variation control crank 308 pointer I06 may be moved through the exact required number of degrees by a reference to the variation scale 3M and index mark and, therefore, the indication of compass I0! will vary from the assumed heading of the trainer by the amount of the variation introduced into the system. The student in the trainer will then be forced to take this variation into account in properly heading the trainer.

When the embodiment of my variation system now being considered is used, variation control crank 308 and variation scale 3M are preferably located at the desk 35. This arrangement provides a more convenient means for the operator for setting the correct variation into the compass system.

It will be realized, therefore, that my previously disclosed systems provide means whereby the operator may introduce into the compass system in a grounded aviation trainer a variation equal to the variation of the geographical position where the trainer is assumed to be flying. The student in the trainer must make proper correction for this variation, if he is to fly his assumed course, just as the pilot in a real plane must correct for variation in order to fly his desired course.

In Fig. 1 the numbers I65, Ill, I15, 2H5 and 222 refer to elements described in detail in my application Serial No. 540,977 filed June 19, 1944, for Radio direction finding means for aviation trainer, which application is a division of this application.

The foregoing being but a preferred embodiment of my invention numerous details may be made in the construction thereof without departing 'from the substance of the invention.

Iclaim: 7

.1 In a grounded aviation trainer thelcombi nation of a fuselage rotatable about a, vertical axis, asimulated magnetic compass indicator in member rotatable with said fuselage, said consaid. fuselage, a control element carried by a trol element determining the readingof said simulated compass indicator, means for pre ent,- ing a rotation of said control element whenever said fuselage. is rotated, and additionaloperable means for changing the position of saidcontrol element. 1 I ,2. In agroundedaviationtrainer the'combination of. a fuselage rotatable about avertical axis, a simulated magnetic compass indicator in said fuselage, a magnet carriediby a member rotatable With said fuselage, said magnet determining the reading of said simulated compass indicater, means for preventing a rotation of. said magnet whenever said fuselage is: ,rotated,.and additional operable means for; changing the, t0- sitionofsaidmagnet. i

3. Ina grounded aviation trainer the combination of a fuselage rotatably mountedupona stationary base, asimulated magnetic compass indicator in said fuselage, a control element car,- ried by a member rotatable with said fuselage, said control element determining the reading. of saidgsimulated compass indicator, means op erated by the rotation of said fueslage with respect to the stationary base vfor preventing :a rotation of said control element whenever:saidfuselage is rotated, and additional operable means for changing the position or said control element.

4. In a grounded aviation training device of the type comprising a fuselage rotatably mounted upon a stationary base, a system for simulating the operation of a real magnetic compass in a plane, said system comprising, in combination, a simulated magnetic compass indicator located inside said fuselage and including a graduated dial and an index element, one of said two last-mentioned parts being movable relative to the other, take-off means operated by the rotation of said fuselage relative to said stationary base and operatively connected to the movable part of said indicator for changing the relative positions of said dial and index element, and additional means connected to the movable part of said indicator for changing the relative positions of said dial and index element.

5. In a grounded aviation training device of the type comprising a fuselage rotatably mounted upon a stationary base, a system for simulating the operation of a real magnetic compass in a plane, said system comprising, in combination, a simulated magnetic compass indicator located inside said fuselage and including a graduated dial and an index element, one of said two lastmentioned parts being movable relative to the other, take-off means operated by the rotation of said fuselage relative to said stationary base and operatively connected to the movable part of said indicator for changing the relative positions of said dial and index element, and additional means comprising a manually operable member and an associated graduated scale both located outside said fuselage for changing the relative positions of said dial and index element according to the magnetic variation at the assumed geographical location of said trainer.

6. In a grounded aviation training device of the type comprising a fuselage rotatably mount- 1;:121 ed u on" afstat'iofiaryrbase, a syst m fdr simulatmg the operation or a. real magnetic compass "in aplalle, said system comprising, in combination, a; sim'iill'ated T'meijgfietic 'cbmpassl indicator heated inside "saidffus'elai'ge, and including a graduated 1 scale :amr ifidx elemhtifone bf Said two lastmentioned pali'ts beiri'g; mdv'able' relative to fthe :brhr,'f'amelebtricat' transmitting system including atransmjitter and a." receiver, said receiver being re pm1s1 e5 to"'theppere;ti0n "of said "transmitter 9,150., cbnneeiqed; tothe"movable-"part7 01" six-id infdicatqr, ftcke=6fi means TOp'erateq by {the- 'rofiait'ic'm ofsaid-"fuse1age relative to said statitinary base and operatively connected to saidinensmittefi'for -pperat-ing the examine 1 in response to a rotation-bf said"fuselage'relative to said-'= stationary base, "and-additional "movable means {connected "to f'sai-d transmitter for j Operating the same.

binationjw simulated? magnetic compass-indica- Certificate of Correction Patent No. 2,445,673. July 20, 1948.

KARL A. KAIL It is hereby certified that error appears in the printed specification of the above numbered patent requiring correction as follows:

Column 10, lines 7 and 8, claim 1, strike out rne'mber rotatable with said fuselage, said consaid fuselage, a control element carried by a and insert instead saidjuselage, a control element carried by a member rotatable with said fuselage, said conand that the said Letters Patent should be read with this correction therein that the same may conform to the record of the ease in the Patent Ofiice.

Signed and sealed this 25th day of January, A. D. 1949.

THOMAS F. MURPHY,

Assistant Gammz'ssioner of Patents. 

